WO2006029888A1 - Structure for separating the internal areas of a high pressure and a low pressure turbine - Google Patents

Structure for separating the internal areas of a high pressure and a low pressure turbine Download PDF

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Publication number
WO2006029888A1
WO2006029888A1 PCT/EP2005/009996 EP2005009996W WO2006029888A1 WO 2006029888 A1 WO2006029888 A1 WO 2006029888A1 EP 2005009996 W EP2005009996 W EP 2005009996W WO 2006029888 A1 WO2006029888 A1 WO 2006029888A1
Authority
WO
WIPO (PCT)
Prior art keywords
disk
series
pins
disks
housings
Prior art date
Application number
PCT/EP2005/009996
Other languages
French (fr)
Inventor
Mario Pecchioli
Dino Bianchi
Original Assignee
Nuovo Pignone S.P.A.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Nuovo Pignone S.P.A. filed Critical Nuovo Pignone S.P.A.
Priority to CA2580476A priority Critical patent/CA2580476C/en
Priority to US11/575,426 priority patent/US7874790B2/en
Priority to JP2007531694A priority patent/JP4646039B2/en
Priority to AT05792235T priority patent/ATE477401T1/en
Priority to DE602005022899T priority patent/DE602005022899D1/en
Priority to KR1020077008606A priority patent/KR101228272B1/en
Priority to CN2005800311423A priority patent/CN101035966B/en
Priority to EP05792235A priority patent/EP1799967B1/en
Publication of WO2006029888A1 publication Critical patent/WO2006029888A1/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/28—Arrangement of seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F01D25/145—Thermally insulated casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor

Definitions

  • the present invention relates to a convex sealing bottom for a twin-shaft gas turbine.
  • a gas turbine is a rotating thermal machine which converts the enthalpy of a gas into useful work, using gases coming from a combustion and which supplies me ⁇ chanical power on a rotating shaft.
  • the turbine therefore normally comprises a compres- sor or turbo-compressor, inside which the air taken from the outside is brought under pressure.
  • Various injectors feed the fuel which is mixed with the air to form a air-fuel ignition mixture.
  • the axial compressor is entrained by a so-called turbine, or turbo-expander, which supplies mechanical en ⁇ ergy to a user transforming the enthalpy of the gases combusted in the combustion chamber.
  • the expansion jump is subdivided into two partial jumps, each of which takes place inside a turbine.
  • the high-pressure turbine downstream of the combustion cham ⁇ ber, entrains the compression.
  • the low-pressure turbine which collects the gases coming from the high-pressure turbine, is then connected to a user.
  • the gas has low-pressure and low-temperature characteristics, whereas, as it passes through the compressor, the gas is compressed and its temperature increases.
  • the heat necessary for the temperature increase of the gas is supplied by the combustion of gas fuel intro ⁇ quizd into the heating chamber, by means of injectors.
  • the triggering of the combustion, when the machine is activated, is obtained by means of sparking plugs.
  • the high- pressure and high-temperature gas reaches the turbine, through specific ducts, where it gives up part of the en ⁇ ergy accumulated in the compressor and heating chamber (combustor) and then flows outside by means of the dis ⁇ charge channels.
  • the internal area of the high pressure turbine and the internal area of the low pressure turbine are sepa ⁇ rated by means of a bottom whose function is to guarantee a sealing between each other. This is to avoid the drawing of gases which would jeopardize the reliability and performances of the power turbine.
  • the bottom also acts as a duct for a flow of so-called "purge” air, i.e. a flow of pressurized air which prevents the ingestion of hot gases through the duct to ⁇ wards the bottom and towards the components of the tur ⁇ bine which would be damaged by these hot gases.
  • the convex bottom currently comprises two convex disks constrained to each other by means of a series of pins.
  • These disks have an outer shaped edge which are cou ⁇ pled, forming a seal, of the metal on metal type, with a sealing ring.
  • said two disks define a channel for the purge air towards the low pressure turbine.
  • One of the disadvantages of the bottoms of known turbines is that, as a result of thermal gradients, they undergo deformations which cause seal losses in the areas where the seal is obtained by means of specific geome- tries.
  • a further disadvantage is that, in this way, there is the ingestion of hot gases which jeopardize the useful life of the bottom and other components of the gas tur ⁇ bine. This is because oxidation phenomena are created at hot temperatures which, accompanied by fatigue phenomena, intensify the stress causing, with time, cracks and splitting, finally jeopardizing the correct functioning of the bottom and other components.
  • An objective of the present invention is to provide a bottom for a twin-shaft turbine which maintains a seal without causing mechanical stress on the bottom itself.
  • a further objective is to provide a convex ⁇ sealing bottom for a twin-shaft turbine which allows an increase in the performances of the turbine itself, maintaining a high useful life of the bottom itself.
  • Yet another objective is to provide a convex sealing bottom for a twin-shaft turbine which avoids the inges ⁇ tion of hot gases coming both from a low pressure turbine and a high pressure turbine.
  • An additional objective is to provide a convex seal ⁇ ing bottom for a twin-shaft turbine which is simple and economical .
  • figure 1 is a raised sectional side view of a pre- ferred embodiment of a bottom of a twin-shaft turbine ac ⁇ cording to the present invention
  • figure 2 is an exploded raised perspective right side view of the bottom of figure 1.
  • these show a convex sealing bottom 10 for a twin-shaft turbine having a high pressure turbine and a low pressure turbine, said bottom 10 comprises a series of disks, in particular three con ⁇ vex disks constrained to and distanced from each other by means of a series of pins arranged in series orthogonally to a base surface of each disks of said three disks.
  • Each pin of said series of pins respectively con ⁇ strains two disks of said series of disks and is arranged orthogonally to these so as to prevent their relative movements in an axial direction, i.e. in a direction par- allel to the axis of the gas turbine, during the func ⁇ tioning of the gas turbine.
  • each pin is orthogonal to a base surface of each of the two disks in which it is inserted, so as to prevent or in any case minimize the relative movements between the two disks in an axial direction, thus maintaining a seal with a nozzle-holder ring 70.
  • each pin allows the disks to which it is constrained, to move in a radial direction so that the disks can freely adapt themselves to the thermal de- formations without generating stress on the disks them ⁇ selves.
  • each pin in the area in which it is constrained, is orthogonal to a base surface of each disk to which it is constrained, in particular it is orthogonal to a portion of the base surface around which it is constrained to the disks.
  • Said series of disks are three convex disks and are respectively a first disk 12, a second disk 13 and a third disk 14.
  • Said three disks are arranged along the axis of the machine and have an outer circular shaped edge 15 which is engaged to obtain the axial seal, of the metal-on- metal type, on a corresponding annular surface 71 of an inner grooved surface 72 of said ring 70 coaxial with the axis of the turbine.
  • Each annular surface 71 is also orthogonal to the axis of the turbine.
  • Each disk of said three disks preferably comprises a series of housings 40 for said series of pins 20 and 21.
  • Said housings 40 are situated on each disk close to the outer circular shaped edge 15.
  • Said housings 40 are preferably bushings welded or brazed to each disk which are distributed at an equidis- tance along a circumference arranged on a base surface of each disk.
  • Said first disk 12 has a central opening 16 and said second disk 13 correspondingly has a central opening 17.
  • Said third disk 14 is situated between said first disk 12 and said second disk 13 and together with these, defines a first channel 61 and a second channel 62, re- spectively.
  • Said first channel 61 and said second channel 62 have the function of bringing air under pressure (purge air) downstream of the high pressure turbine and upstream of the low pressure turbine respectively, avoiding the ingestion of hot gases which could damage the components of the turbine.
  • Said bottom 10 comprises a series of spokes 30 welded to said three disks in corresponding central por ⁇ tions of each of these.
  • Each disk of said three disks comprises a series of pass-through cuts 18 situated on a base surface and ar ⁇ ranged radially, equidistant and uniformly distributed along a circumference of said base surface.
  • Said series of spokes 30 are inserted in the corre- sponding series of cuts 18 of each disk of said three disks and made integral preferably by means of welding or brazing.
  • Said series of pins comprises a first series of pins
  • said first series of pins 20 constrains said first disk 12 to said third disk 14, whereas said second series of pins 21 constrains said second disk 13 to said third disk 14.
  • said first series of pins 20 is pref ⁇ erably angularly dephased with respect to second series of pins 21 by an angle preferably of 15° .
  • Said first series of pins 20 and said second series of pins 21 each preferably comprise twelve round-headed pins.
  • the first disk 12 and the second disk 13 conse- quently, each comprise 12 welded or brazed bushings, as housings for the first series of pins 20 and for the sec ⁇ ond series of pins 21, respectively.
  • the third disk 14 consequently comprises 24 welded or brazed bushings as housings for the first series of pins 20 and for the second series of pins 21, respec ⁇ tively.
  • Said bottom 10 moreover, comprises an insulating element 80 applied on the first disk 12.
  • Said insulating element has a disk form having a central hole 81 for the passage of a stream of air fed through the opening 16.
  • a convex sealing bottom for a twin-shaft turbine achieves the purposes specified above.
  • the convex sealing bottom for a twin-shaft turbine of the present invention thus conceived can undergo nu ⁇ merous modifications and variants, all included in the same inventive concept.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
  • Glass Compositions (AREA)
  • Flanged Joints, Insulating Joints, And Other Joints (AREA)
  • Cable Accessories (AREA)

Abstract

Convex sealing bottom (10) for a twin-shaft turbine of the type comprising a series of convex disks constrained to each other by means of a series of pins, each disk of said disks comprises an outer shaped edge which is engaged with a corresponding annular surface (71) of an inner grooved surface (72) of a ring (70) for obtaining an axial seal. The series of disks comprises three disks, a first disk (12), a second disk (13) and a third disk (14) respectively. The three disks are fixed to each other centrally by means of a series of spokes (30) and are constrained in pairs respectively by means of a series of pins which are arranged orthogonally to the three disks to minimize the relative movements of the three disks in an axial direction at the same time allowing the radial dilatations of the three disks themselves.

Description

STRUCTURE FOR SEPARATING THE INTERNAL AREAS OF A HIGH PRESSURE AND A LOW PRESSURE TURBINE
The present invention relates to a convex sealing bottom for a twin-shaft gas turbine. A gas turbine is a rotating thermal machine which converts the enthalpy of a gas into useful work, using gases coming from a combustion and which supplies me¬ chanical power on a rotating shaft.
The turbine therefore normally comprises a compres- sor or turbo-compressor, inside which the air taken from the outside is brought under pressure.
Various injectors feed the fuel which is mixed with the air to form a air-fuel ignition mixture.
The axial compressor is entrained by a so-called turbine, or turbo-expander, which supplies mechanical en¬ ergy to a user transforming the enthalpy of the gases combusted in the combustion chamber.
In applications for the generation of mechanical en¬ ergy, the expansion jump is subdivided into two partial jumps, each of which takes place inside a turbine. The high-pressure turbine, downstream of the combustion cham¬ ber, entrains the compression. The low-pressure turbine, which collects the gases coming from the high-pressure turbine, is then connected to a user. The turbo-expander, turbo-compressor, combustion chamber (or heater) , outlet shaft, regulation system and ignition system, form the essential parts of a gas tur¬ bine plant .
As far as the functioning of a gas turbine is con- cerned, it is known that the fluid penetrates the com¬ pressor through a series of inlet ducts.
In these canalizations, the gas has low-pressure and low-temperature characteristics, whereas, as it passes through the compressor, the gas is compressed and its temperature increases.
It then penetrates into the combustion (or heating) chamber, where it undergoes a further significant in¬ crease in temperature.
The heat necessary for the temperature increase of the gas is supplied by the combustion of gas fuel intro¬ duced into the heating chamber, by means of injectors.
The triggering of the combustion, when the machine is activated, is obtained by means of sparking plugs.
At the outlet of the combustion chamber, the high- pressure and high-temperature gas reaches the turbine, through specific ducts, where it gives up part of the en¬ ergy accumulated in the compressor and heating chamber (combustor) and then flows outside by means of the dis¬ charge channels. In applications for the generation of mechanical en¬ ergy, the internal area of the high pressure turbine and the internal area of the low pressure turbine are sepa¬ rated by means of a bottom whose function is to guarantee a sealing between each other. This is to avoid the drawing of gases which would jeopardize the reliability and performances of the power turbine.
The bottom also acts as a duct for a flow of so- called "purge" air, i.e. a flow of pressurized air which prevents the ingestion of hot gases through the duct to¬ wards the bottom and towards the components of the tur¬ bine which would be damaged by these hot gases.
The convex bottom currently comprises two convex disks constrained to each other by means of a series of pins.
These disks have an outer shaped edge which are cou¬ pled, forming a seal, of the metal on metal type, with a sealing ring.
Furthermore, said two disks define a channel for the purge air towards the low pressure turbine. One of the disadvantages of the bottoms of known turbines is that, as a result of thermal gradients, they undergo deformations which cause seal losses in the areas where the seal is obtained by means of specific geome- tries.
The reason for this is that when the turbine is run¬ ning, the pins, initially axially oriented, rotate spe¬ cifically as a result of non-uniform thermal deformations on the disks, jeopardizing the correct seal on the seal- ing ring.
A further disadvantage is that, in this way, there is the ingestion of hot gases which jeopardize the useful life of the bottom and other components of the gas tur¬ bine. This is because oxidation phenomena are created at hot temperatures which, accompanied by fatigue phenomena, intensify the stress causing, with time, cracks and splitting, finally jeopardizing the correct functioning of the bottom and other components. An objective of the present invention is to provide a bottom for a twin-shaft turbine which maintains a seal without causing mechanical stress on the bottom itself.
A further objective is to provide a convex ■sealing bottom for a twin-shaft turbine which allows an increase in the performances of the turbine itself, maintaining a high useful life of the bottom itself.
Yet another objective is to provide a convex sealing bottom for a twin-shaft turbine which avoids the inges¬ tion of hot gases coming both from a low pressure turbine and a high pressure turbine.
An additional objective is to provide a convex seal¬ ing bottom for a twin-shaft turbine which is simple and economical .
These objectives according to the present invention are achieved by providing a convex sealing bottom for a twin-shaft turbine as specified in claim 1.
Further characteristics of the invention are indi¬ cated in the subsequent claims .
The characteristics and advantages of a convex seal- ing bottom for a twin-shaft gas turbine according to the present invention will appear more evident from the fol¬ lowing illustrative and non-limiting description, refer¬ ring to the schematic drawings enclosed, in which: figure 1 is a raised sectional side view of a pre- ferred embodiment of a bottom of a twin-shaft turbine ac¬ cording to the present invention; figure 2 is an exploded raised perspective right side view of the bottom of figure 1.
With reference to the figures, these show a convex sealing bottom 10 for a twin-shaft turbine having a high pressure turbine and a low pressure turbine, said bottom 10 comprises a series of disks, in particular three con¬ vex disks constrained to and distanced from each other by means of a series of pins arranged in series orthogonally to a base surface of each disks of said three disks.
Each pin of said series of pins respectively con¬ strains two disks of said series of disks and is arranged orthogonally to these so as to prevent their relative movements in an axial direction, i.e. in a direction par- allel to the axis of the gas turbine, during the func¬ tioning of the gas turbine.
In other words, each pin is orthogonal to a base surface of each of the two disks in which it is inserted, so as to prevent or in any case minimize the relative movements between the two disks in an axial direction, thus maintaining a seal with a nozzle-holder ring 70.
At the same time, each pin allows the disks to which it is constrained, to move in a radial direction so that the disks can freely adapt themselves to the thermal de- formations without generating stress on the disks them¬ selves.
This is possible as each pin, in the area in which it is constrained, is orthogonal to a base surface of each disk to which it is constrained, in particular it is orthogonal to a portion of the base surface around which it is constrained to the disks.
The reason for this is to avoid possible states of stress on the disks themselves which could jeopardize the correct functioning and useful life of the convex bottom 10.
Said series of disks are three convex disks and are respectively a first disk 12, a second disk 13 and a third disk 14.
Said three disks are arranged along the axis of the machine and have an outer circular shaped edge 15 which is engaged to obtain the axial seal, of the metal-on- metal type, on a corresponding annular surface 71 of an inner grooved surface 72 of said ring 70 coaxial with the axis of the turbine. Each annular surface 71 is also orthogonal to the axis of the turbine.
Each disk of said three disks preferably comprises a series of housings 40 for said series of pins 20 and 21.
Said housings 40 are situated on each disk close to the outer circular shaped edge 15.
Said housings 40 are preferably bushings welded or brazed to each disk which are distributed at an equidis- tance along a circumference arranged on a base surface of each disk. Said first disk 12 has a central opening 16 and said second disk 13 correspondingly has a central opening 17.
Said third disk 14 is situated between said first disk 12 and said second disk 13 and together with these, defines a first channel 61 and a second channel 62, re- spectively.
Said first channel 61 and said second channel 62 have the function of bringing air under pressure (purge air) downstream of the high pressure turbine and upstream of the low pressure turbine respectively, avoiding the ingestion of hot gases which could damage the components of the turbine.
Said bottom 10 comprises a series of spokes 30 welded to said three disks in corresponding central por¬ tions of each of these. Each disk of said three disks comprises a series of pass-through cuts 18 situated on a base surface and ar¬ ranged radially, equidistant and uniformly distributed along a circumference of said base surface.
Said series of spokes 30 are inserted in the corre- sponding series of cuts 18 of each disk of said three disks and made integral preferably by means of welding or brazing.
Said series of pins comprises a first series of pins
20 and a second series of pins 21, said first series of pins 20 constrains said first disk 12 to said third disk 14, whereas said second series of pins 21 constrains said second disk 13 to said third disk 14.
Furthermore, said first series of pins 20 is pref¬ erably angularly dephased with respect to second series of pins 21 by an angle preferably of 15° .
Said first series of pins 20 and said second series of pins 21 each preferably comprise twelve round-headed pins.
The first disk 12 and the second disk 13 conse- quently, each comprise 12 welded or brazed bushings, as housings for the first series of pins 20 and for the sec¬ ond series of pins 21, respectively.
The third disk 14 consequently comprises 24 welded or brazed bushings as housings for the first series of pins 20 and for the second series of pins 21, respec¬ tively.
By means of a series of round-headed pins arranged orthogonally to said disks, it is advantageously possible to allow the disks themselves to radially dilate without generating stress.
Said bottom 10, moreover, comprises an insulating element 80 applied on the first disk 12.
Said insulating element has a disk form having a central hole 81 for the passage of a stream of air fed through the opening 16. By means of a bottom for a twin-shaft turbine ac¬ cording to the present invention, it is advantageously possible to have two ducts or channels for respective two streams of pressurized air (purge air) , each of which is fed from outside the machine towards the low pressure turbine and towards the high pressure turbine respec¬ tively.
In this way, it is advantageously possible to avoid the ingestion of hot gases also coming from the high pressure turbine protecting the life of the components of the turbine and its reliability.
It can thus be seen that a convex sealing bottom for a twin-shaft turbine according to the present invention achieves the purposes specified above. The convex sealing bottom for a twin-shaft turbine of the present invention thus conceived can undergo nu¬ merous modifications and variants, all included in the same inventive concept.
Furthermore, in practice, the materials used, as also the dimensions and components, can vary according to technical demands.

Claims

1. A convex sealing bottom (10) for a twin-shaft tur¬ bine of the type comprising a series of convex disks, constrained to each other by means of a series of pins, each disk of said disks comprises an outer shaped edge which is engaged with a corresponding annular surface (71) of an inner grooved surface (72) of a ring (70) for obtaining an axial seal, characterized in that said se¬ ries of disks are three disks, a first disk (12) , a sec- ond disk (13) and a third disk (14) respectively, and in that said three disks are fixed to each other centrally by means of a series of spokes (30) and in that they are constrained in pairs respectively by means of said series of pins which are arranged orthogonally to said three disks to minimize the relative movements of said three disks in an axial direction at the same time allowing the radial dilatations of said three disks.
2. The bottom (10) according to claim 1, characterized in that each disk of said three disks comprises a series of housings (40) for said series of pins (20) and (21) .
3. The bottom (10) according to claim 1 or 2, charac¬ terized in that said series of housings (40) is situated on each disk of said three disks along a circumference close to the outer circular shaped edge (15) .
4. The bottom (10) according to any of the claims from 1 to 3, characterized in that said housings (40) are bushings welded to each disk which are distributed at an equidistance along a circumference arranged on a base surface of each disk.
5. The bottom (10) according to any of the claims from 1 to 4, characterized in that said first disk (12) has a central opening (16) and said second disk (13) corre¬ spondingly has a central opening (17) .
6. The bottom (10) according to any of the claims from 1 to 5, characterized in that said third disk (14) is situated between said first disk (12) and said second disk (13) and with these defines a first duct (61) and a second duct (62) respectively for respective two streams of pressurized air fed from outside the machine towards a high pressure turbine and towards a low pressure turbine respectively.
7. The bottom (10) according to any of the claims from 1 to 6, characterized in that each disk of said three disks comprises a series of pass-through cuts (18) situ- ated on a base surface and arranged radially, equidistant and uniformly distributed along a circumference of said base surface.
8. The bottom (10) according to any of the claims from 1 to 7, characterized in that said bottom (10) comprises a series of spokes (30) inserted in a corresponding se- ries of cuts (18) of each disk of said three disks and welded to said three disks in corresponding central por¬ tions of each of these.
9. The bottom (10) according to any of the claims from 1 to 8, characterized in that it comprises a first series of pins (20) and a second series of pins (21) with a round head, said first series of pins (20) constrains said first disk (12) to said third disk (14) , whereas said second series of pins (21) constrains said second disk (13) to said third disk (14) .
10. The bottom (10) according to claim 9, characterized in that the pins of said first series of pins (20) and said second series of pins (21) are distributed at a equidistance on a base circumference of each disk of said three disks.
11. The bottom (10) according to claim 9 or 10, charac¬ terized in that the pins of said first series of pins (20) is angularly dephased with respect to said second series of pins (21) preferably by an angle of 15°.
12. The bottom (10) according to any of the claims from 9 to 11, characterized in that said first series of pins (20) and said second series of pins (21) each comprise twelve round-headed pins.
13. The bottom (10) according to any of the claims from 9 to 12, characterized in that said first disk (12) and said second disk (13) each comprise twelve bushings re¬ spectively as housings for the first series of pins (20) and for the second series of pins (21) and in that said third disk (14) comprises twenty-four bushings respec- tively as housings for said first series of pins (20) and for said second series of pins (21) .
14. The bottom (10) according to any of the claims from 1 to 13, characterized in that it comprises an insulating element (80) applied to said first disk (12) .
PCT/EP2005/009996 2004-09-17 2005-09-14 Structure for separating the internal areas of a high pressure and a low pressure turbine WO2006029888A1 (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
CA2580476A CA2580476C (en) 2004-09-17 2005-09-14 Structure for separating the internal areas of a high pressure and a low pressure turbine
US11/575,426 US7874790B2 (en) 2004-09-17 2005-09-14 Convex sealing bottom for a twin-shaft turbine
JP2007531694A JP4646039B2 (en) 2004-09-17 2005-09-14 A structure that separates the internal regions of high and low pressure turbines.
AT05792235T ATE477401T1 (en) 2004-09-17 2005-09-14 STRUCTURE FOR SEPARATING THE INTERIOR AREAS OF A HIGH PRESSURE AND LOW PRESSURE TURBINE
DE602005022899T DE602005022899D1 (en) 2004-09-17 2005-09-14 STRUCTURE FOR DISCONNECTING THE INTERIORS OF A HIGH PRESSURE AND LOW PRESSURE BIN
KR1020077008606A KR101228272B1 (en) 2004-09-17 2005-09-14 Structure for separating the internal areas of a high pressure and a low pressure turbine
CN2005800311423A CN101035966B (en) 2004-09-17 2005-09-14 Structure for separating the internal areas of a high pressure and a low pressure turbine
EP05792235A EP1799967B1 (en) 2004-09-17 2005-09-14 Structure for separating the internal areas of a high pressure and a low pressure turbine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IT001778A ITMI20041778A1 (en) 2004-09-17 2004-09-17 BOTTOM SEALED BOTTOM FOR A DOUBLE SHAFT TURBINE
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Publication number Priority date Publication date Assignee Title
CA2828313C (en) * 2011-02-28 2015-01-27 Alstom Technology Ltd. Turbine comprising a sealing device between the stator blade carrier and the housing
DE102014214775A1 (en) * 2014-07-28 2016-01-28 Rolls-Royce Deutschland Ltd & Co Kg Aircraft gas turbine with a seal for sealing a spark plug on the combustion chamber wall of a gas turbine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1318275A2 (en) * 2001-12-10 2003-06-11 Nuovo Pignone Holding S.P.A. Structure for separating the high and low pressure turboexpanders of a gas turbine
EP1359364A1 (en) * 2002-04-29 2003-11-05 Nuovo Pignone Holding S.P.A. Sealing device for a pipe leading through an opening in a wall
US20040037699A1 (en) * 2000-07-03 2004-02-26 Franco Frosini Connecting system for a transition duct in a gas turbine

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5307622A (en) * 1993-08-02 1994-05-03 General Electric Company Counterrotating turbine support assembly
US6619030B1 (en) * 2002-03-01 2003-09-16 General Electric Company Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors
US6684626B1 (en) * 2002-07-30 2004-02-03 General Electric Company Aircraft gas turbine engine with control vanes for counter rotating low pressure turbines

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040037699A1 (en) * 2000-07-03 2004-02-26 Franco Frosini Connecting system for a transition duct in a gas turbine
EP1318275A2 (en) * 2001-12-10 2003-06-11 Nuovo Pignone Holding S.P.A. Structure for separating the high and low pressure turboexpanders of a gas turbine
EP1359364A1 (en) * 2002-04-29 2003-11-05 Nuovo Pignone Holding S.P.A. Sealing device for a pipe leading through an opening in a wall

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CN101035966B (en) 2010-12-08
DE602005022899D1 (en) 2010-09-23
ATE477401T1 (en) 2010-08-15
ITMI20041778A1 (en) 2004-12-17
KR101228272B1 (en) 2013-01-30
CN101035966A (en) 2007-09-12
CA2580476A1 (en) 2006-03-23
US20070257440A1 (en) 2007-11-08
JP4646039B2 (en) 2011-03-09
KR20070057951A (en) 2007-06-07
EP1799967B1 (en) 2010-08-11
JP2008513661A (en) 2008-05-01
CA2580476C (en) 2014-04-15
EP1799967A1 (en) 2007-06-27
US7874790B2 (en) 2011-01-25

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